GOE 228 (MVA H.38) AIRFOIL (goe228-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 228 (MVA H.38) AIRFOIL (goe228-il) Reynolds number: 200,000 Max Cl/Cd: 70.64 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe228-il-200000.txt Download as CSV file: xf-goe228-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 228 (MVA H.38) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 0.0029 0.09300 0.08933 -0.1245 0.9386 0.0886
-10.000 0.0240 0.09101 0.08733 -0.1222 0.9330 0.0896
-9.750 -0.1748 0.04915 0.04496 -0.1589 0.9075 0.0587
-9.500 -0.1801 0.04404 0.03953 -0.1651 0.8975 0.0585
-9.250 -0.1694 0.03924 0.03415 -0.1714 0.8910 0.0588
-9.000 -0.1450 0.03513 0.02959 -0.1759 0.8878 0.0596
-8.750 -0.1324 0.03327 0.02760 -0.1754 0.8785 0.0602
-8.500 -0.1033 0.03124 0.02541 -0.1771 0.8745 0.0611
-8.250 -0.0712 0.02944 0.02344 -0.1790 0.8715 0.0624
-8.000 -0.0508 0.02835 0.02219 -0.1787 0.8633 0.0638
-7.750 -0.0204 0.02681 0.02036 -0.1801 0.8584 0.0656
-7.500 0.0132 0.02535 0.01855 -0.1817 0.8549 0.0670
-7.250 0.0374 0.02408 0.01713 -0.1816 0.8475 0.0682
-7.000 0.0659 0.02290 0.01595 -0.1820 0.8417 0.0703
-6.750 0.0986 0.02196 0.01492 -0.1829 0.8376 0.0731
-6.500 0.1245 0.02133 0.01417 -0.1827 0.8297 0.0757
-6.250 0.1542 0.02031 0.01304 -0.1831 0.8235 0.0783
-6.000 0.1865 0.01931 0.01207 -0.1839 0.8191 0.0821
-5.750 0.2116 0.01884 0.01156 -0.1835 0.8097 0.0868
-5.500 0.2430 0.01790 0.01063 -0.1843 0.8037 0.0935
-5.250 0.2716 0.01727 0.00999 -0.1846 0.7957 0.1023
-5.000 0.3023 0.01658 0.00932 -0.1854 0.7880 0.1157
-4.750 0.3336 0.01596 0.00875 -0.1862 0.7807 0.1360
-4.500 0.3634 0.01533 0.00824 -0.1869 0.7714 0.1694
-4.250 0.3953 0.01482 0.00797 -0.1880 0.7638 0.2446
-4.000 0.4237 0.01483 0.00797 -0.1879 0.7536 0.2863
-3.750 0.4532 0.01490 0.00790 -0.1879 0.7445 0.3118
-3.500 0.4818 0.01495 0.00789 -0.1878 0.7344 0.3317
-3.250 0.5098 0.01504 0.00788 -0.1877 0.7235 0.3482
-2.750 0.5662 0.01493 0.00763 -0.1874 0.7018 0.3707
-2.500 0.5942 0.01493 0.00754 -0.1873 0.6904 0.3820
-2.250 0.6230 0.01487 0.00737 -0.1873 0.6798 0.3923
-2.000 0.6502 0.01490 0.00729 -0.1871 0.6672 0.4026
-1.750 0.6775 0.01486 0.00722 -0.1869 0.6554 0.4108
-1.500 0.7061 0.01492 0.00711 -0.1870 0.6450 0.4211
-1.250 0.7327 0.01495 0.00712 -0.1867 0.6333 0.4303
-1.000 0.7602 0.01507 0.00712 -0.1866 0.6224 0.4414
-0.750 0.7877 0.01515 0.00713 -0.1865 0.6126 0.4516
-0.500 0.8143 0.01526 0.00719 -0.1863 0.6017 0.4620
-0.250 0.8419 0.01537 0.00722 -0.1863 0.5928 0.4697
0.000 0.8686 0.01550 0.00729 -0.1862 0.5832 0.4796
0.250 0.8961 0.01565 0.00740 -0.1862 0.5751 0.4882
0.500 0.9226 0.01581 0.00751 -0.1860 0.5663 0.4989
0.750 0.9505 0.01601 0.00765 -0.1860 0.5590 0.5090
1.000 0.9760 0.01617 0.00785 -0.1857 0.5506 0.5214
1.250 1.0039 0.01641 0.00798 -0.1858 0.5436 0.5364
1.500 1.0292 0.01662 0.00825 -0.1854 0.5360 0.5506
1.750 1.0555 0.01682 0.00845 -0.1852 0.5292 0.5666
2.000 1.0830 0.01710 0.00867 -0.1852 0.5232 0.5847
2.250 1.1077 0.01731 0.00895 -0.1848 0.5164 0.6041
2.500 1.1342 0.01755 0.00914 -0.1846 0.5104 0.6252
2.750 1.1598 0.01781 0.00941 -0.1843 0.5044 0.6455
3.000 1.1838 0.01800 0.00968 -0.1837 0.4980 0.6649
3.250 1.2100 0.01822 0.00987 -0.1835 0.4926 0.6845
3.500 1.2355 0.01848 0.01015 -0.1832 0.4875 0.7042
3.750 1.2589 0.01869 0.01045 -0.1826 0.4821 0.7242
4.000 1.2838 0.01889 0.01067 -0.1822 0.4771 0.7453
4.250 1.3113 0.01915 0.01089 -0.1823 0.4724 0.7676
4.500 1.3311 0.01931 0.01122 -0.1810 0.4671 0.7926
4.750 1.3519 0.01940 0.01143 -0.1797 0.4621 0.8344
5.000 1.3740 0.01945 0.01153 -0.1787 0.4579 1.0000
5.250 1.4020 0.01989 0.01190 -0.1791 0.4539 1.0000
5.500 1.4251 0.02027 0.01233 -0.1787 0.4497 1.0000
5.750 1.4500 0.02065 0.01270 -0.1785 0.4458 1.0000
6.000 1.4763 0.02103 0.01304 -0.1786 0.4424 1.0000
6.250 1.5056 0.02147 0.01337 -0.1792 0.4392 1.0000
6.500 1.5284 0.02194 0.01389 -0.1787 0.4360 1.0000
6.750 1.5496 0.02238 0.01442 -0.1779 0.4326 1.0000
7.000 1.5727 0.02281 0.01488 -0.1775 0.4293 1.0000
7.250 1.5974 0.02322 0.01528 -0.1773 0.4263 1.0000
7.500 1.6243 0.02364 0.01566 -0.1775 0.4236 1.0000
7.750 1.6524 0.02416 0.01615 -0.1779 0.4208 1.0000
8.000 1.6673 0.02467 0.01680 -0.1761 0.4175 1.0000
8.250 1.6851 0.02514 0.01737 -0.1747 0.4141 1.0000
8.500 1.7062 0.02560 0.01787 -0.1740 0.4111 1.0000
8.750 1.7300 0.02603 0.01830 -0.1737 0.4084 1.0000
9.000 1.7577 0.02646 0.01871 -0.1740 0.4058 1.0000
9.250 1.7791 0.02705 0.01937 -0.1734 0.4032 1.0000
9.500 1.7887 0.02768 0.02015 -0.1708 0.4005 1.0000
9.750 1.8011 0.02829 0.02088 -0.1686 0.3976 1.0000
10.000 1.8174 0.02886 0.02153 -0.1671 0.3949 1.0000
10.250 1.8376 0.02936 0.02208 -0.1663 0.3924 1.0000
10.500 1.8633 0.02973 0.02245 -0.1664 0.3898 1.0000
10.750 1.8816 0.03032 0.02309 -0.1653 0.3865 1.0000
11.000 1.8775 0.03127 0.02423 -0.1609 0.3830 1.0000
11.250 1.8809 0.03199 0.02506 -0.1576 0.3785 1.0000
11.500 1.8969 0.03228 0.02533 -0.1562 0.3739 1.0000
11.750 1.9105 0.03290 0.02598 -0.1546 0.3697 1.0000
12.000 1.9042 0.03425 0.02754 -0.1506 0.3659 1.0000
12.250 1.9074 0.03529 0.02869 -0.1479 0.3616 1.0000
12.500 1.9204 0.03585 0.02926 -0.1464 0.3573 1.0000
12.750 1.9283 0.03682 0.03030 -0.1444 0.3529 1.0000
13.000 1.9181 0.03877 0.03245 -0.1407 0.3482 1.0000
13.250 1.9196 0.04009 0.03387 -0.1384 0.3431 1.0000
13.500 1.9331 0.04076 0.03449 -0.1372 0.3379 1.0000
13.750 1.9184 0.04346 0.03745 -0.1339 0.3332 1.0000
14.000 1.9140 0.04553 0.03964 -0.1316 0.3276 1.0000
14.250 1.9213 0.04674 0.04083 -0.1302 0.3217 1.0000
14.500 1.9051 0.05022 0.04456 -0.1277 0.3159 1.0000
14.750 1.9025 0.05256 0.04697 -0.1261 0.3094 1.0000
15.000 1.8927 0.05585 0.05041 -0.1245 0.3024 1.0000
15.250 1.8825 0.05934 0.05401 -0.1232 0.2943 1.0000
15.500 1.8684 0.06352 0.05833 -0.1220 0.2858 1.0000
15.750 1.8588 0.06726 0.06211 -0.1211 0.2766 1.0000
16.000 1.8364 0.07292 0.06796 -0.1205 0.2666 1.0000
16.250 1.8165 0.07839 0.07352 -0.1200 0.2552 1.0000
16.500 1.7943 0.08425 0.07944 -0.1198 0.2424 1.0000
16.750 1.7712 0.09035 0.08556 -0.1198 0.2287 1.0000
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Polar data table (+)
Polar graphs
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